EP3090952B1 - Triebwerksgondel - Google Patents

Triebwerksgondel Download PDF

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Publication number
EP3090952B1
EP3090952B1 EP16160912.8A EP16160912A EP3090952B1 EP 3090952 B1 EP3090952 B1 EP 3090952B1 EP 16160912 A EP16160912 A EP 16160912A EP 3090952 B1 EP3090952 B1 EP 3090952B1
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EP
European Patent Office
Prior art keywords
plasma
leading surface
nacelle
air flowing
actuators
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Active
Application number
EP16160912.8A
Other languages
English (en)
French (fr)
Other versions
EP3090952A1 (de
Inventor
Roy David Fulayter
Crawford F. Smith Iii
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Rolls Royce Corp
Rolls Royce North American Technologies Inc
Original Assignee
Rolls Royce Corp
Rolls Royce North American Technologies Inc
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Publication date
Application filed by Rolls Royce Corp, Rolls Royce North American Technologies Inc filed Critical Rolls Royce Corp
Publication of EP3090952A1 publication Critical patent/EP3090952A1/de
Application granted granted Critical
Publication of EP3090952B1 publication Critical patent/EP3090952B1/de
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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02K—JET-PROPULSION PLANTS
    • F02K1/00—Plants characterised by the form or arrangement of the jet pipe or nozzle; Jet pipes or nozzles peculiar thereto
    • F02K1/38—Introducing air inside the jet
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C23/00—Influencing air flow over aircraft surfaces, not otherwise provided for
    • B64C23/005—Influencing air flow over aircraft surfaces, not otherwise provided for by other means not covered by groups B64C23/02 - B64C23/08, e.g. by electric charges, magnetic panels, piezoelectric elements, static charges or ultrasounds
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENTS OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
    • B64D33/00—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for
    • B64D33/02—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for of combustion air intakes
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D17/00—Regulating or controlling by varying flow
    • F01D17/10—Final actuators
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
    • F01D25/24—Casings; Casing parts, e.g. diaphragms, casing fastenings
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENTS OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
    • B64D33/00—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for
    • B64D33/02—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for of combustion air intakes
    • B64D2033/0226—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for of combustion air intakes comprising boundary layer control means
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2220/00—Application
    • F05D2220/30—Application in turbines
    • F05D2220/32—Application in turbines in gas turbines
    • F05D2220/323—Application in turbines in gas turbines for aircraft propulsion, e.g. jet engines
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F15—FLUID-PRESSURE ACTUATORS; HYDRAULICS OR PNEUMATICS IN GENERAL
    • F15D—FLUID DYNAMICS, i.e. METHODS OR MEANS FOR INFLUENCING THE FLOW OF GASES OR LIQUIDS
    • F15D1/00—Influencing flow of fluids
    • F15D1/002—Influencing flow of fluids by influencing the boundary layer
    • F15D1/0065—Influencing flow of fluids by influencing the boundary layer using active means, e.g. supplying external energy or injecting fluid
    • F15D1/0075—Influencing flow of fluids by influencing the boundary layer using active means, e.g. supplying external energy or injecting fluid comprising electromagnetic or electrostatic means for influencing the state of the fluid, e.g. for ionising the fluid or for generating a plasma

Claims (14)

  1. Gondel für ein Strahltriebwerk (10), Folgendes beinhaltend
    eine innere Fläche (28), welche eine Öffnung zum Einströmen von Luft in einen Motoreinlass definiert,
    eine äußere Fläche (30), welche außerhalb der inneren Fläche positioniert ist,
    eine vordere Fläche (32), welche die Öffnung umgreift, wobei die vordere Fläche die innere Fläche und die äußere Fläche verbindet, wobei die vordere Fläche eine Stagnationslinie (34) definiert, und
    mindestens ein Plasmastellglied (42), welches positioniert ist, um den Luftstrom über der vorderen Fläche zu unterbrechen, um laminare Trennung von Luft, welche in den Motoreinlass strömt, zu reduzieren,
    dadurch gekennzeichnet, dass das mindestens eine Plasmastellglied (42) an der vorderen Fläche (32) positioniert und an der Stagnationslinie (34) zentriert ist.
  2. Gondel nach Anspruch 1, bei welcher das mindestens eine Plasmastellglied eine Vielzahl von Plasmastellgliedern beinhaltet, welche um die Öffnung an der vorderen Fläche der Gondel positioniert sind, wobei die Vielzahl von Plasmastellgliedern entlang der Stagnationslinie ausgefluchtet ist.
  3. Gondel nach Anspruch 1, bei welcher das mindestens eine Plasmastellglied konfiguriert ist, um den der über die vordere Fläche strömenden Luft vermittelten Schwung zu variieren.
  4. Gondel nach Anspruch 3, bei welcher das mindestens eine Plasmastellglied eine Vielzahl von Plasmastellgliedern beinhaltet, welche um die Öffnung an der vorderen Fläche positioniert sind, wobei jedes der Vielzahl von Plasmastellgliedern unabhängig bedienbar ist, um den der über die vordere Fläche an jedem der Plasmastellglieder strömenden Luft vermittelten Schwung zu steuern, wobei optionsweise die Vielzahl von Plasmastellgliedern entlang der Stagnationslinie ausgefluchtet ist.
  5. Gondel nach Anspruch 1, bei welcher das mindestens eine Plasmastellglied an der vorderen Fläche positioniert ist.
  6. Gondel nach Anspruch 5, bei welcher das mindestens eine Plasmastellglied variabel ist, um den Grad des vermittelten Schwungs zu erhöhen, um den Luftstrom zu unterbrechen, wobei optionsweise das mindestens eine Plasmastellglied eine Vielzahl von Plasmastellgliedern beinhaltet, welche um die Öffnung an der vorderen Fläche der Gondel positioniert sind, wobei jedes der Vielzahl von Plasmastellgliedern unabhängig bedienbar ist, um den der Luft über die vordere Fläche an jedem Plasmastellglied strömenden Luft vermittelten Schwung zu steuern.
  7. Gondel nach Anspruch 1, bei welcher der Luftstrom zum Motoreinlass im Allgemeinen parallel zur Drehachse des Motors ist und die Gondel zudem eine Vielzahl von Plasmastellgliedern beinhaltet, wobei jedes Plasmastellglied positioniert ist, um einen Luftstrom zu unterbrechen, der eine Richtung aufweist, die schräg zur Drehachse des Motors ist.
  8. Gondel nach Anspruch 7, bei welcher die Plasmastellglieder an der vorderen Fläche positioniert und entlang der Stagnationslinie ausgefluchtet sind.
  9. Gondel nach Anspruch 8, bei welcher jedes der Vielzahl von Plasmastellgliedern konfiguriert ist, um den der über die vordere Fläche strömenden Luft vermittelten Schwung zu variieren, wobei optionsweise die Vielzahl von Plasmastellgliedern so konfiguriert ist, dass jedes Plasmastellglied unabhängig arbeiten kann, um den der über die vordere Fläche strömenden Luft vermittelten Schwung zu variieren.
  10. Gondel nach Anspruch 7, bei welcher jedes der Vielzahl von Plasmastellgliedern konfiguriert ist, um den der in den Lufteinlass des Motors strömenden Luft vermittelten Schwung zu variieren.
  11. Gondel nach Anspruch 10, bei welcher jedes der Vielzahl von Plasmastellgliedern konfiguriert ist, um den der über die vordere Fläche strömenden Luft vermittelten Schwung zu variieren, wobei optionsweise die Vielzahl von Plasmastellgliedern so konfiguriert ist, dass jedes Plasmastellglied unabhängig arbeiten kann, um den der über die vordere Fläche strömenden Luft vermittelten Schwung zu variieren.
  12. Gondel nach Anspruch 1, beinhaltend eine Vielzahl von Plasmastellgliedern, welche an der vorderen Fläche positioniert sind, um Luftstrom über die vordere Fläche in eine Richtung zu unterbrechen, die nicht parallel zur Fahrtrichtung des Strahltriebwerks ist.
  13. Gondel nach Anspruch 12, bei welcher jedes der Vielzahl von Plasmastellgliedern konfiguriert ist, um den der in den Lufteinlass des Motors strömenden Luft vermittelten Schwung zu variieren.
  14. Gondel nach Anspruch 13, bei welcher jedes der Vielzahl von Plasmastellgliedern konfiguriert ist, um den der über die vordere Fläche strömenden Luft vermittelten Schwung zu variieren, wobei optionsweise die Vielzahl von Plasmastellgliedern so konfiguriert ist, dass jedes Plasmastellglied unabhängig arbeiten kann, um den der über die vordere Fläche strömenden Luft vermittelten Schwung zu variieren.
EP16160912.8A 2015-03-31 2016-03-17 Triebwerksgondel Active EP3090952B1 (de)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
US201562140901P 2015-03-31 2015-03-31

Publications (2)

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EP3090952A1 EP3090952A1 (de) 2016-11-09
EP3090952B1 true EP3090952B1 (de) 2018-10-03

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EP16160912.8A Active EP3090952B1 (de) 2015-03-31 2016-03-17 Triebwerksgondel

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US (1) US10273903B2 (de)
EP (1) EP3090952B1 (de)
CA (1) CA2925323A1 (de)

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US20190316613A1 (en) * 2018-04-17 2019-10-17 GM Global Technology Operations LLC Internal flow control using plasma actuators
CN109606707A (zh) * 2018-10-26 2019-04-12 南京理工大学 一种基于等离子体流动控制的宽域超声速进气道

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US4749150A (en) 1985-12-24 1988-06-07 Rohr Industries, Inc. Turbofan duct with noise suppression and boundary layer control
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US5447283A (en) 1994-02-02 1995-09-05 Grumman Aerospace Corporation Blown boundary layer control system for a jet aircraft
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US7744039B2 (en) * 2006-01-03 2010-06-29 The Boeing Company Systems and methods for controlling flows with electrical pulses
US7637455B2 (en) * 2006-04-12 2009-12-29 The Boeing Company Inlet distortion and recovery control system
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FR2924407B1 (fr) 2007-12-03 2010-05-14 Airbus France Systeme de sortie d'air pour un bord d'attaque d'aeronef
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US9975625B2 (en) * 2010-04-19 2018-05-22 The Boeing Company Laminated plasma actuator
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Publication number Publication date
US10273903B2 (en) 2019-04-30
US20160290282A1 (en) 2016-10-06
CA2925323A1 (en) 2016-09-30
EP3090952A1 (de) 2016-11-09

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